CN102785058A - components with precision surface channels and hybrid machining method - Google Patents
components with precision surface channels and hybrid machining method Download PDFInfo
- Publication number
- CN102785058A CN102785058A CN201210166868XA CN201210166868A CN102785058A CN 102785058 A CN102785058 A CN 102785058A CN 201210166868X A CN201210166868X A CN 201210166868XA CN 201210166868 A CN201210166868 A CN 201210166868A CN 102785058 A CN102785058 A CN 102785058A
- Authority
- CN
- China
- Prior art keywords
- groove
- substrate
- coating
- grooves
- structure coating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/182—Transpiration cooling
- F01D5/183—Blade walls being porous
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/11—Manufacture by removing material by electrochemical methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/13—Manufacture by removing material using lasers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/14—Micromachining
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
- Y10T428/24273—Structurally defined web or sheet [e.g., overall dimension, etc.] including aperture
- Y10T428/24322—Composite web or sheet
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T83/00—Cutting
- Y10T83/02—Other than completely through work thickness
- Y10T83/0304—Grooving
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
Methods of forming one or more grooves in a component are provided. One method includes using a first machining technique to form one or more preliminary grooves in an outer surface of a substrate. Each preliminary groove has a base and extends at least partially along the outer surface of the substrate, and the substrate has an inner surface that defines at least one hollow, interior space. The method further includes using a second machining technique to further machine the preliminary groove(s) to form the respective groove(s). In addition, the method includes forming one or more access holes through the base of a respective groove to connect the respective groove in fluid communication with the respective hollow interior space (114). Components with grooves comprise a sidewall radius R in a range of 0 R 0.127 mm.
Description
Technical field
The present invention relates generally to gas-turbine unit, exactly, relates to the microchannel cooling in the gas-turbine unit.
Background technology
In gas-turbine unit, air compresses in compressor, subsequently in the combustion chamber with fuel mix, to produce hot combustion gas.From pressure turbine (HPT) but gas the energy Driven Compressor that obtains, the energy that from the gas of low-pressure turbine (LPT), obtains can drive the fan in the turbofan aircraft engine application, also can drive the outer shaft in boats and ships and the commercial Application.
Engine efficiency increases with the rising of burning gas temperature.But combustion gas is known from experience the various parts in heating respective flow passage/stream, therefore, need cool off to prolong the life-span of engine.Generally, come the cooling hot gas passage component through the air of from compressor, discharging.Because the air of discharging is not used for combustion process, therefore, this cooling procedure has reduced engine efficiency.
The gas-turbine unit cooling technology is comparatively ripe, and comprises the multinomial patent to the various aspects of cooling circuit in the various hot gas path components and characteristic.For example, the combustion chamber comprises outside and interior lining/bushing pipe radially, and these outsides and inner liner need cool off in operation.Turbomachine injection nozzle comprises the hollow blade that is supported between tyre (outer bands) and the interior band (inner bands), also need cool off.Turbine rotor blade is hollow, wherein generally includes cooling circuit, and blade by the turbine protective cover around, it need cool off equally.Hot combustion gas is discharged via exhaust apparatus, and said exhaust apparatus also can be provided with liner/lining and carry out suitable cooling.
In this type of exemplary combustion turbine engine components, use the thin metallic walls that constitutes by the high strength superalloy to increase durability at all usually, reduce the cooling requirement of this base part simultaneously to greatest extent.Various cooling circuits and characteristic can suitably be adjusted to this type of particular component that is in the respective environment in the engine.For example, can in hot gas path component, form a series of internal cooling channel, i.e. serpentine channel (serpentines).Can cooling fluid be provided to serpentine channel from high-tension room, said cooling fluid will flow through said passage, thus the substrate of cooling hot gas passage component and coating.But this cooling strategy causes heat transfer rate relatively low usually, and part temperatures distribution/profile is uneven.
Through making cooling as far as possible near heat affected zone, the microchannel cooling might significantly reduce cooling requirement, thereby under the given situation of heat transfer rate, reduces the hot side of main carrying substrate material and the temperature difference of cold side.But, be to realize the microchannel cooling, passage should have sharp edge (sharp edges), helping with free from flaw mode plating (flaw free deposition) first metal (structure) coating, and reduces or eliminates and possibly cause the interface space of ftractureing.
Therefore, a kind of method need be provided, be used to form microchannel, helping, and reduce or eliminate and to cause the interface space of ftractureing with free from flaw mode plating first structure coating with sharp edge.In addition, also a kind of method need be provided, be used to form the microchannel that variation reduces between the shortening of processing procedure time, the channel-to-channel.
Summary of the invention
One side of the present invention provides a kind of method that is used for forming at parts one or more grooves.Said method comprises uses first process technology, in the outer surface of substrate, forms one or more preliminary grooves.Each preliminary groove have the bottom and at least part extend along the said outer surface of said substrate, and said substrate has inner surface, said inner surface is provided with at least one internal cavities.Said method further comprises uses second process technology that said preliminary groove is further processed, to form corresponding recesses.In addition, said method comprises the one or more entering of formation hole, and the bottom of corresponding recesses is passed in said entering hole, corresponding recesses is communicated with stream with corresponding internal cavities or claims that the mode of fluid connection is connected.
Said method further is included in the said outer surface of said substrate and forms before said one or more preliminary grooves, casts said substrate.Said first process technology comprises that abrasion liquid sprays, and wherein said one or more preliminary groove forms through the said outer surface that makes the abrasion liquid jet act on said substrate.Said second process technology is by selecting in following the group that forms: the spark machined (milling EDM) and the Laser Processing (laser drill) of electrochemistry processing (ECM), electrical discharge machining (EDM), use rotation electrode.Said second process technology comprises milling EDM.Each groove in said one or more groove has the top; Each groove that wherein uses said abrasion liquid to spray in the said one or more preliminary grooves that form has the bottom of being wider than said top; So that each groove in said one or more preliminary groove comprise in curved preliminary groove; And said top is wider than in the said bottom of wherein said groove, so that each groove in said one or more groove comprises the introversion connected in star.
Said method further comprises: before implementing said first process technology; Fugitive coating is plated on the said outer surface of said substrate; Wherein said substrate is processed through said fugitive coating, and wherein said being processed in forms one or more openings in the said fugitive coating; With after implementing said second process technology, remove said fugitive coating.Said method further is included in and forms before said one or more preliminary grooves; Structure coating is plated on the said outer surface of said substrate; The formation method of wherein said one or more preliminary grooves is; Implement said first process technology processing, thereby in said structure coating, form one or more openings via said structure coating; And the formation method of wherein said one or more grooves is to implement said second process technology via the said one or more openings in the said structure coating.Said method is heat-treated after further being included in the said structure coating of plating.Said structure coating is through implementing one or multinomial formation in following: plasma plating, thermal spray method and cold method of spray plating.Said method further comprises: before implementing said first process technology; Fugitive coating is plated on the said structure coating; Wherein said substrate and said structure coating are processed through said fugitive coating, and wherein said being processed in forms one or more openings in the said fugitive coating; With after implementing said second process technology, remove said fugitive coating.
Another aspect of the present invention is to provide a kind of method that is used for forming at parts one or more grooves.Said method comprises structure coating is plated on the outer surface of substrate that wherein said substrate has at least one internal cavities.Said method further comprises uses first process technology, in said structure coating, forms one or more preliminary grooves.Each preliminary groove has bottom and the said substrate extension in part edge at least.Said method further comprises uses second process technology that said preliminary groove is further processed, in said structure coating, to form corresponding one or more grooves.In addition, said method comprises the one or more entering of formation hole, and the bottom of corresponding recesses is passed in said entering hole, so that corresponding recesses is connected with the stream mode of communicating with corresponding internal cavities.
Said method further is included in the said structure coating and forms before said one or more preliminary grooves, casts said substrate.Said first process technology comprises that abrasion liquid sprays, and wherein said one or more preliminary groove forms through making the abrasion liquid jet act on said structure coating.Said second process technology is by selecting in following the group that forms: the spark machined (milling EDM) and the Laser Processing (laser drill) of electrochemistry processing (ECM), electrical discharge machining (EDM), use rotation electrode.Said second process technology comprises milling EDM.Each groove in said one or more groove has the top; Each groove that wherein uses said abrasion liquid to spray in the said one or more preliminary grooves that form has the bottom of being wider than said top so that each groove in said one or more preliminary groove comprise in curved preliminary groove; And said top is wider than in the said bottom of wherein said groove, so that each groove in said one or more groove comprises the introversion connected in star.
Said method further comprises: before implementing said first process technology; Fugitive coating is plated on the said structure coating; Wherein said structure coating is processed through said fugitive coating, and wherein said being processed in forms one or more openings in the said fugitive coating; With after implementing said second process technology, remove said fugitive coating.Said method is heat-treated after further being included in the said structure coating of plating.Said structure coating is through implementing or the multinomial plating that carries out in following: plasma plating, thermal spray method and cold method of spray plating.Use at least one steps of said first and second process technologies to comprise and be worked in the said substrate, so that said one or more groove extends in the said substrate.
Another aspect of the present invention is to provide a kind of parts, and said parts comprise the substrate with outer surface and inner surface, and wherein said inner surface is provided with at least one internal cavities.Said outer surface is provided with one or more grooves, and each groove at least part extend and have a bottom along the said outer surface of said substrate.Each groove is characterised in that, the sidewall radius R is in the scope of 0＜R＜0.127 millimeter.The bottom of corresponding recesses is passed in one or more entering hole, so that said groove is communicated with corresponding internal cavities stream.Said parts further comprise coating, and it is arranged at least a portion of said outer surface of said substrate and above groove, extends, so that said groove is formed for cooling off one or more passages of said parts with said coating.
Each groove in said one or more groove has the top, and said top is wider than in wherein said bottom, so that each groove in said one or more groove comprises the introversion connected in star.Said coating comprises first and second structure coatings at least; Wherein said first structure coating does not extend on said one or more grooves; And wherein said second structure coating is arranged on said first structure coating and on said one or more grooves and extends, so that said one or more groove and said second structure coating form said one or more cooling duct together.
Another aspect of the present invention is to provide a kind of parts, and said parts comprise the substrate with outer surface and inner surface, and wherein said inner surface is provided with at least one internal cavities.Said parts further comprise the structure coating at least a portion of the said outer surface that is arranged on said substrate.Said structure coating is provided with one or more grooves, and each groove part at least extends and has a bottom along said substrate.The said bottom of corresponding recesses is passed in one or more entering hole, so that said groove is communicated with corresponding internal cavities stream.Each groove is characterised in that, the sidewall radius R is in the scope of 0＜R＜0.127 millimeter.Said parts further comprise at least one additional coatings, and it is arranged on above said structure coating top and the said groove, so that said groove is configured for cooling off one or more passages of said parts with said additional coatings.At least one outlet opening passes the additional coatings of each respective channel, to receive and to discharge coolant fluid from said respective channel.
Each groove in said one or more groove has the top, and said top is wider than in wherein said bottom, so that each groove in said one or more groove comprises the introversion connected in star.Said additional coatings comprises second structure coating.Said groove passes said structure coating and extends in the said substrate.
Description of drawings
Consult specify below the advantages after, can understand better of the present invention these with other characteristics, aspect and advantage, in the accompanying drawings, similar similar part in the symbology institute drawings attached, wherein:
Fig. 1 is the sketch map of gas turbine system;
Fig. 2 is the schematic cross-section with configurations of tabs instance of cooling duct;
Fig. 3 is various aspects according to the present invention to Fig. 5, uses the hybrid process method in substrate, to form the sketch map of the method step of groove;
Fig. 6 is various aspects according to the present invention to Fig. 8, uses the hybrid process method in substrate, to form the sketch map of the method step of introversion groove (re-entrant grooves);
Fig. 9 is various aspects according to the present invention to Figure 11, in substrate, forms the sketch map of the method step of groove with fugitive being coated with (fugitive coating) layer through the hybrid process method;
Figure 12 is various aspects according to the present invention to Figure 15, uses the hybrid process method in substrate, to form the sketch map of the method step of groove through structure coating;
Figure 16 is various aspects according to the present invention to Figure 18, uses the hybrid process method in structure coating, to form the sketch map of the method step of groove;
Figure 19 describes the perspective view of three passage instances with the sketch map mode, wherein said tunnel-shaped be formed in the said substrate and with coolant feed to corresponding film-cooling hole;
Figure 20 is the sectional view of a passage in the passage instance shown in Figure 19, has wherein shown cooling agent from getting into the microchannel that the hole is transported to film-cooling hole; And
Figure 21 is being formed in the structure coating, having a schematic cross-section of the configurations of tabs instance of cooling duct of various aspects according to the present invention.
The component symbol tabulation:
| Reference number | Parts | | Parts | |
| 10 | |
12 | |
|
| 14 | The |
16 | |
|
| 18 | |
20 | |
|
| 30 | Fugitive coating | 32 | The |
|
| 34 | Opening in the fugitive coating | 50 | |
|
| 54 | |
56 | |
|
| 58 | Be formed at the opening in first structure coating | 80 | Hot |
|
| 100 | Hot |
110 | Substrate |
| 112 | The outer surface of |
114 | Internal cavities |
| 116 | The inner surface of |
130 | |
| 131 | |
132 | |
| 134 | The bottom of |
135 | The sidewall of groove/ |
| 136 | The top of groove (opening) | 140 | Get into the |
| 142 | |
160 | The abrasion |
| 165 | Rotation electrode (being used for milling EDM) | 234 | The bottom of |
| 236 | The top of preliminary groove |
The specific embodiment
The used term of this specification " first ", " second " etc. are not represented any order, quantity or importance, but are used to distinguish different elements.The used term of this specification " one " and " one " do not represent restricted number, but there be at least one in the reference items in expression.The determiner relevant with quantity " pact " comprises setting value, and has the indicated meaning of context (for example, comprising the degree of error relevant with the measurement of specific quantity).In addition, term " composition " comprises admixture, mixture, alloy, product etc.
In addition, in this manual, suffix " (s) " is intended to comprise the odd number and the plural number of the term that limits usually, therefore, can comprise one or more (for example, except as otherwise noted, otherwise " opening " can comprise one or more openings) of this term." embodiment ", " another embodiment ", " embodiment " that specification is mentioned in full wait be meant comprise among described at least one the embodiment of this specification combine said embodiment description element-specific (for example; Characteristic, structure and/or characteristic), said element-specific can exist or can not be present among other embodiment.In addition, should be appreciated that said inventive features can make up in any suitable manner in multinomial embodiment.
Fig. 1 is the sketch map of gas turbine system 10.Said system 10 can comprise one or more compressor 12, combustion chamber 14, turbine 16 and fuel nozzle 20.Compressor 12 can be connected through one or more axles 18 with turbine 16.Axle 18 can be single shaft or is joined together to form the multiaxis section of axle 18.
When hot gas path component 100 was exposed to thermal current 80, hot gas path component 100 was heated by thermal current 80, and possibly reach the temperature that hot gas path component 100 is broken down.Therefore, in order to let system 10 operate for 80 times at the thermal current of high temperature, thereby the efficient of raising system 10 and performance need a kind of cooling system that is used for hot gas path component 100.
Generally, cooling system of the present invention comprises a series of passage aisles or microchannel, and it is formed in the surface of hot gas path component 100.Power generation turbine parts for industrial size; " little " or micro-channel size possibly comprise 0.25 millimeter to 1.5 millimeters approximate depth and the width in the scope; And for the turbine components of aviation size, channel size possibly comprise 0.15 millimeter to 0.5 millimeter approximate depth and the width in the scope.Hot gas path component can be provided with protective layer (cover layer).Can cooling fluid be provided to said passage from high-tension room, said cooling fluid will flow through said passage with cooling protective layer.
Consult Fig. 2 and be described in the method that forms one or more grooves 132 in the parts 100 to Figure 15.As shown in the figure, for example, in Fig. 3, said method comprises uses first process technology, in the outer surface 112 of substrate 110, forms one or more preliminary grooves 131.For instantiation shown in Figure 3, use abrasion liquid jet (abrasive liquid jet) 160 to form preliminary groove, this technology will specify below.As shown in Figure 4, each preliminary groove 131 has bottom 134, and for example like Figure 19 and shown in Figure 20, each preliminary groove 131 at least partly extends along the outer surface 112 of substrate 110.As shown in the figure, for example in Fig. 2, substrate 110 has inner surface 116, and said inner surface 116 is provided with at least one internal cavities 114.
In the surface 112 of substrate 110, form before the preliminary groove 131, usually substrate 110 is cast.According to the 5th, 626, the introduction in No. 462 United States Patent (USP) cases, substrate 110 can be made up of any suitable material.According to the intended use of parts 100, that said material can comprise is Ni-based, cobalt-based and iron-based superalloy.Nickel-base heat resisting superalloy can be that those contain γ and γ ' material mutually, and particularly those contain γ and γ ' nickel-base heat resisting superalloy mutually, and wherein γ ' occupies at least 40% of said superalloy total amount mutually.Because this type of alloy has various desirable properties (comprising elevated temperature strength and high-temperature creep resistance) simultaneously, therefore has very much advantage.The substrate material also can comprise alloy between the nickel aluminum metal, because generally acknowledge that these alloys have multiple advantageous property simultaneously, comprises elevated temperature strength and high-temperature creep resistance, and these advantageous properties make this type of alloy use very advantageous at the turbogenerator that is used for aircraft.Under the situation of using niobium-base alloy; With preferably using the good alloy that is coated with the niobium base of non-oxidizability, especially those comprise the alloy (wherein compositing range is represented with atomic percent) of Nb-(27-40) Ti-(4.5-10.5) Al-(4.5-7.9) Cr-(1.5-5.5) Hf-(0-6) V.The substrate material also can comprise niobium-base alloy, and said niobium-base alloy contains at least one time looks (secondary phase), for example, comprises the compound between niobium metal that contains of silicide, carbide or boride.This type of alloy is the synthetic of ductility phase (ductile phase) (being the niobium base) and hardening constituent (promptly containing compound between niobium metal).For other layouts, the substrate material comprises molybdenum-base alloy, for example has Mo5SiB2 and Mo3Si second molybdenum-base alloy (solid solution (solid solution)) mutually.For other structures, the substrate material comprises the ceramic base synthetic, the carborundum of for example strengthening with the SiC fiber (SiC) matrix.For other structures, the substrate material comprises the titanium aluminum based metal compound.
As shown in the figure, for example in Fig. 4, said method further comprises uses second process technology that one or more preliminary grooves 131 are further processed, to form corresponding one or more groove 132.For instantiation shown in Figure 4, use rotation electrode (spinning electrode) 165 to come preliminary groove further to be processed through the milling electrical discharge machining (EDM), be described below.
For method instance shown in Figure 5; Component manufacturing method further comprises the one or more entering of formation hole 140; The bottom 134 of the corresponding recesses in the groove 132 is passed in said entering hole 140, is communicated with so that form stream between groove 132 and the corresponding internal cavities 114.Get into hole 140 and forming preliminary groove 131 back formation usually, but before first process operation, form, or between first and second process operation, form.The cross section that gets into hole 140 is generally circular or oval, and for example, can use one or multinomial formation in following: Laser Processing (laser drill), the injection of abrasion liquid, EDM and electron-beam drilling.Get into hole 140 and can use first or second process technology, or use such as other process technology formation such as laser drill.Getting into hole 140 generally speaking can, can hole with 134 one-tenth 20 modes of spending an angle of 90 degrees of bottom portion of groove perpendicular to the bottom 134 (as shown in Figure 5) of corresponding recesses 132.
As stated, for method instance shown in Figure 5, first process technology comprises that abrasion liquid sprays, and preliminary groove 131 forms through the outer surface 112 that makes abrasion liquid jet 160 act on substrate 110.The title of submitting on May 28th, 2010 is the 12/790th of the co-assigned of " comprising object of chevron film-cooling hole and associated method (Articles which include chevron film cooling holes; and related processes) " the; The instance of water-jet boring method and system is provided in No. 675 patent application, and wherein said U.S. Patent application way of reference is in full incorporated in the present patent application.Of the 12/790th, No. 675 patent application, the water-jet method is used high speed abrasive particle (for example abrasion " grains of sand ") stream usually, and wherein said abrasive particle is suspended in the High-Pressure Water.But the hydraulic pressure marked change, but in about 35 to 620MPa scopes, change usually.Can use multiple abrasive material, for example garnet, aluminium oxide, carborundum and bead.
In addition, of the 12/790th, No. 675 U.S. Patent application, the water-jet system can comprise multiaxis computer numerical control (CNC) unit.Said CNC system is that prior art is known, and for example is being described in No. 2005/0013926 U.S. Patent No. application (S Lu Kesiji people such as (S.Rutkowski)), and said U.S. Patent application is incorporated in this specification with way of reference.The CNC system can make cutting element move along a plurality of X, Y and Z axle and rotating shaft.Advantageously, preliminary groove 131 can be about 0.75 millimeter passage of taking advantage of 0.75 millimeter through make the abrasion liquid jet be used to form area of section with the linear velocity up to 2.5 centimetres of per seconds.But possibly not have high accuracy and uniform width owing to using abrasion liquid to spray the preliminary groove 131 that forms, possibly lack required sharp edge on groove-coating interface simultaneously, therefore use second process technology to come groove 132 is carried out fine finishining.
Can use various processing methods to come as second process technology.For example, second process technology can be selected in by the following group that forms: electrochemistry processing (ECM), EDM, milling EDM (adopting the EDM of rotation electrode 165) and Laser Processing (laser drill).Particularly, if select ECM, can carry out etching or carry out impouring (plunge) ECM via the electric insulation protective cover.Title is that the 6th, 644, No. 921 United States Patent (USP)s (BAKE people such as (Bunker)) of " cooling duct and manufacturing approach " are described the ECM method that receives impulse action, and wherein said United States Patent (USP) is incorporated in this specification with way of reference.In brief, receive the ECM of impulse action to use the ECM method in the following manner: to stop in need not to remove the zone of material with the electrode with patterning protective cover and process.For impouring ECM, need not to use protective cover.Carry out before first process operation if use protective cover, then said method further are included in, electric insulation protective cover (not shown) is plated on the substrate; Use abrasion liquid to spray and form preliminary groove; And carry out etching to form groove via said protective cover subsequently.As stated, the 6th, 644, No. 921 United States Patent (USP)s have been described through carrying out etching via protective cover and have been accomplished ECM.
In Fig. 3 and method instance shown in Figure 4, second process technology comprises milling EDM.Advantageously, milling EDM can control on groove/coating interface, forming required edge well.For ad hoc approach, also use milling EDM to form and get into hole 140.For example, preliminary groove 131 can use abrasion liquid to spray and form, and is as shown in Figure 3.Subsequently, can use milling EDM to form and get into hole 140, and groove 132 is polished.Perhaps, can use milling EDM to come at first groove 132 to be polished/fine finishining, form then and get into hole 140.
As stated, the abrasion liquid injection system can comprise multiaxis CNC unit (not shown).Arrange for certain, can with rotation electrode 165 be installed to processing platform or with the used similar device of liquid jet 160 on.For these structures; Can be through using with the used similar machining prgraming of liquid injection to come rotation electrode 165 is controlled; Thereby the rotation electrode is advanced along passage; And oppose side wall carries out " cleaning " so that it is vertical, and removes any one-tenth rounded edges (any edge radiusing) that liquid jet method produces.This milling EDM method can be used as single step each passage is implemented, and wherein milling EDM tool diameter is enough big, just in time to be engaged in channel interior.But because the liquid injection channel possibly not have high accuracy and uniform width, so milling EDM can divide two stages to carry out, and on each channel side wall 135, carries out once.In this latter event, milling EDM tool diameter can be little many, therefore do not influence the moulding that double teeming is made equally.This also will be implemented in channel width variation aspect and have the free degree greatly, thereby milling EDM method and tighter tolerances (tight tolerances) are separated.Milling EDM instrument need not to extend to the bottom of passage, and need not so for specific embodiment.The main target of milling EDM operation is to form sharp edge in channel roof.Therefore, can programme with " removing " these edges to CNC, and the remainder that makes sidewall 135 out of plumb slightly, like Fig. 4 and shown in Figure 5.That is to say that sidewall 135 can have into the sharp edge of prespecified geometric, for example vertical or angled.
Advantageously, based on the accurate processing of milling EDM, the speed (therefore having reduced manufacturing cost) that this hybrid process method provides abrasion liquid to spray.In this way, the inventive method provides required sharp edge, to help with free from flaw mode plating first metal coating.In addition, can manipulate similar parts datum mark and programming to these two, perhaps can be based on programming to other process technologies to the programming of a process technology.
Fig. 6 explains the method step that uses the hybrid process method in substrate 110, to form introversion groove (re-entrant grooves) 132 to Fig. 8 with the sketch map mode.For example as shown in Figure 6; For this method; Each preliminary groove 131 is to use abrasion liquid jet 160 to form, and has the bottom 234 of being wider than top 236, so that each preliminary groove 131 comprises into the preliminary groove 131 of interior curved shape (re-entrant shaped).In this way, the preliminary groove 131 of curved shape in abrasion liquid jet 160 directly is used to form.In forming, behind the preliminary groove 131 of curved shape, can use various processing methods to be used as second process technology, comprise ECM, EDM, milling EDM (adopting the EDM of rotation electrode 165), and Laser Processing.For layout shown in Figure 7, use milling EDM to come internal curved groove 132 to implement polishing or finishing operations.As shown in Figure 7, after process operation, top 136 is wider than in the bottom 134 of groove 132, so that each groove 132 comprises introversion connected in star 132.Except consulting the described method of Fig. 6 and Fig. 7; The introversion groove can be through forming the preliminary groove as open recess; For example as shown in Figure 3, use EDM or another process technology to come " polishing/fine finishining " top edge then, for example as shown in Figure 4; And use abrasion liquid to spray the bottom of widening groove then, so that groove is curved in forming.
Fig. 9 explains the method step that uses the hybrid process method in substrate 110, to form groove 132 with fugitive coating (fugitive coating) to Figure 11 with the sketch map mode.For example as shown in Figure 9, this method is included in to be carried out before first process operation, fugitive coating 30 is plated on the outer surface 112 of substrate 110.Like Figure 10 and shown in Figure 11, for this method, process, and said being processed in forms one or more openings 34 in the fugitive coating 30 via 30 pairs of substrates 110 of fugitive coating.As title for " using the method (Method of fabricating a component using a fugitive coating) of fugitive coating manufacture component " the 12/943rd; No. 563 U.S. Patent applications (BAKE people such as (Bunker)) are said, and wherein said U.S. Patent application way of reference is in full incorporated in this specification; Fugitive coating 30 is as the processing protective cover that forms passage, and the edge that helps to make the cooling duct 130 of formation on the coating interface, to have sharp keen and sharp outline.
In addition, component manufacturing method optionally further is included in to be carried out before the process operation, and fugitive coating 30 is carried out drying, curing or sintering.For the specific method structure, the thickness that is plated on the fugitive coating 30 on the substrate 110 is in about 0.5 millimeter to 2.0 millimeters scope.In a non-limiting example, fugitive coating 30 comprises that thickness is 1 millimeter the coating based on polymer.Can use various coating technologies to come the fugitive coating 30 of plating, comprise powder coated, electrostatic coating, immersion coating, spin coating, chemical vapor deposition, and use the band of handling through special.Particularly, fugitive coating is basic evenly and can adhere to, but not can handle or the follow-up process that removes in harm substrate 110.
For the ad hoc approach structure, use powder coated or electrostatic coating to come the fugitive coating 30 of plating.For the method construct instance, fugitive coating 30 comprises polymer.For example, fugitive coating 30 can comprise the coating based on polymer, pyridine (pyridine) for example, and this coating can use the method for chemical vapor deposition to carry out plating.Other coating material instances based on polymer comprise resin, for example polyester (polyester) or epoxy resin (epoxies).Examples of resins comprises light-cured resin; For example photocuring or ultraviolet curable resin; These resin non-limiting examples comprise that ultraviolet ray/visible-light curing shelters resin (UV/Visible light curable masking resin); It is sold through trade mark Speedmask 729
by DYMAX company; The said firm is at the Tuo Lingdun of Connecticut, USA (Torrington; Connecticut) have the location of business. in this case, said method further is included in to be carried out before the process operation, and light-cured resin 30 is cured.For additive method/processing procedure structure, fugitive coating 30 comprises carbonaceous material (carbonaceous material).For example, fugitive coating 30 can comprise graphite paint.Polyethylene (polyethylene) is another coating material instance.For the additive method structure, fugitive coating 30 can be the enamel coating (enameled) that is plated on the substrate 110.
Figure 12 explains the method step that uses the hybrid process method in substrate 110, to form groove 132 via structure coating 54 to Figure 15 with the sketch map mode.For example shown in figure 12, this method is included in and forms before the preliminary groove 131, structure coating 54 is plated on the outer surface 112 of substrate 110.The 5th, 640, No. 767 United States Patent (USP)s and the 5th, 626, No. 462 United States Patent (USP)s provide the instance of structure coating, and wherein said United States Patent (USP) way of reference is in full incorporated in this specification.As the 5th, 626, No. 426 United States Patent (USP) is said, and structure coating bonds to the each several part on the surface 112 of substrate 110.For instance constructs, the thickness of structure coating 54 is less than about 1.0 millimeters, exactly, and less than about 0.5 millimeter.For example, use the thickness of the structure coating 54 that the plasma plating forms maybe be, but for hot plasma spraying (for example high-velocity oxy-fuel) coating, the thickness of structure coating 54 maybe be less than about 1 millimeter less than about 0.5 millimeter.
Structure coating can carry out plating through various technology.For ad hoc approach, structure coating carries out plating through plasma plating (cathode arc).Title in co-assigned is the method and apparatus instance that cathode arc plasma plating is provided in No. 20080138529 U.S. Patent No. application (Wei Fuer people such as (Weaver)) of " method and apparatus of cathode arc plasma plating (Method and apparatus for cathodic arc ion plasma deposition) ", and this U.S. Patent application way of reference is in full incorporated in this specification.In brief; The plasma plating comprises the negative electrode that is formed by coating material is placed in the vacuum environment in the vacuum chamber; Substrate 110 is provided in vacuum environment; And to negative electrode supply electric current forming cathode arc at cathode surface, thereby through electric arc coating material is corroded at cathode surface, and the coating material of negative electrode is plated on the substrate surface 112.
For some hot gas path component 100, structure coating comprises Ni-based or cobalt-base alloys, particularly, comprises superalloy or (nickel cobalt) chromium aluminium yttrium ((NiCo) CrAlY) alloy.For example, if the substrate material is to contain γ and γ ' nickel-base heat resisting superalloy mutually, then structure coating can comprise the identical materials composition, like the following United States Patent (USP)s detailed description of consulting the 5th, 626, No. 462.
For the specific method structure, structure coating carries out plating through at least one item in thermal spray method and the cold method of spray plating.For example; The thermal spray method can comprise burning spraying plating or plasma spraying; The burning spraying plating can comprise high-velocity oxy-fuel spraying plating (HVOF) or velocity air fuel spraying plating (HVAF); And plasma spraying can comprise atmosphere (for example air or inert gas) plasma spraying, or low pressure plasma spraying plating (LPPS is also referred to as vacuum plasma spraying plating or VPS).In a limiting examples, the NiCrAlY coating can be carried out plating through HVOF or HVAF.Another technical examples that is used for the plating structure coating includes, but not limited to spraying plating, electro beam physics vapor deposition (electron beam physical vapor deposition), electroless plating, and electroplates.In addition, said method optionally further is included in after the plating structure coating 54 and before carrying out process operation, heat-treats.
Shown in figure 13, for illustrated method, the formation method of preliminary groove 131 is, implements first process technology, processing via structure coating 54, thereby in structure coating 54, forms one or more openings 58.Although clearly do not show, preliminary groove 131 may extend in the substrate 110.Likewise, shown in figure 14, for illustrated method, the formation method of groove 132 is to implement second process technology via the opening in the structure coating 54 58.Although do not show clearly that groove 132 may extend in the substrate 110.Generally, will after accomplishing process operation, second structure coating (not shown) be plated on the said structure coating.Advantageously, use two structure coatings can improve the matching degree of material character and microstructure in the critical passage border region.This can strengthened coat and substrate between bonding, thereby improve the durability of cooling duct.
Although clearly show, the above-mentioned Figure 12 of consulting can further be included in before enforcement first process technology to the described method of Figure 14, and fugitive coating 30 is plated on the structure coating 54.For this method, substrate 110 is processed via fugitive coating 30 with structure coating 54, and said being processed in form one or more openings 34 in the fugitive coating 30, consults Figure 10 and Figure 11 is said like preceding text.This method removes fugitive coating 30 after further being included in and implementing second process technology.But, shown in figure 15, will keep structure coating 54.Fugitive coating 30 will remove before or after forming entering hole 140.Although clearly do not illustrate this ad hoc approach, fugitive coating 30 shown in Figure 9 can be plated on the structure coating shown in Figure 12, and can implement Figure 13 and procedure of processing shown in Figure 14 to two coatings 30,54.As stated; Fugitive coating 30 is as the processing protective cover that forms passage; And for this method, the edge that helps to make the cooling duct 130 of formation on the interface between the structure coating (not shown) of structure coating 54 and follow-up plating, to have necessary sharp keen and sharp outline.
Consult Figure 12 and Figure 16 and be described in the another kind of method that forms one or more grooves 132 in the parts 100 to Figure 18.As shown in the figure, for example in Figure 12, said method comprises structure coating 54 is plated on the outer surface 112 of substrate 110.As shown in the figure, for example in Figure 18, substrate 110 has at least one internal cavities 114.Substrate 110 is as described above with structure coating 54.The instance of coating coating technology comprises plasma plating, thermal spray and cold spraying plating, as stated.Said method is heat-treated after optionally further being included in plating structure coating 54.
Shown in figure 16, said method further comprises uses first process technology in structure coating 54, to form one or more preliminary grooves 131.Of Figure 16, each preliminary groove 131 has bottom 134, and for example like Figure 19 and shown in Figure 20, part is extended along substrate 110 at least.Shown in figure 17, said method further comprises uses second process technology that preliminary groove 131 is further processed, in structure coating 54, to form corresponding recesses 132.For illustrated method, behind the process operation second structure coating 56 is being coated on the structure coating 54.These two structure coatings can comprise identical or different material, and can have identical or different character.
Shown in figure 18, said method further comprises the one or more entering of formation hole 140, and the bottom 134 of the corresponding recesses in the groove 132 is passed in said entering hole 140, so that corresponding recesses 132 is connected with the stream mode of communicating with corresponding internal cavities 114.Get into hole 140 and after forming groove, form usually, but also can form before first process operation or between first and second process operation.As stated, get into hole 140 and can use first or second process technology, or use such as other process technology formation such as laser drill.Equally as stated, use the thickness of the structure coating 54 that the plasma plating forms maybe be, but for hot plasma spraying plating (for example high-velocity oxy-fuel spraying plating) coating, the thickness of structure coating 54 maybe be less than about 1 millimeter less than about 0.5 millimeter.Groove can be completed in structure coating 54, and is of Figure 18, or extends in the substrate 110.
The first and second process technology instances as stated.For illustrated method, first process technology comprises that abrasion liquid sprays, and preliminary groove 131 forms through abrasion liquid jet 160 is acted on the structure coating 54.As stated, the instance of second process technology comprises ECM, EDM, milling EDM, and Laser Processing.Particularly, if select ECM, then can adopt impouring ECM.For ad hoc approach, first process technology comprises that abrasion liquid sprays, and second process technology comprises milling EDM.
Although clearly do not illustrate, can use said method in structure coating 54, to form the introversion connected in star.For example; Can use abrasion liquid jet 160 in structure coating 54, form in curved (consulting Fig. 6) preliminary groove 132; Can use second process technology then comes internal curved groove 132 to polish or claims fine finishining; It is said to Fig. 8 to consult Fig. 6 like preceding text, but the groove of this moment is formed in the structure coating 54.
Although clearly do not illustrate, fugitive coating 30 can be used as the protective cover (mask) when in structure coating, forming groove.For this method, said method further is included in to be implemented before first process technology fugitive coating 30 to be plated on the structure coating 54.For this method, process via 30 pairs of structure coatings 54 of fugitive coating, and said being processed in forms one or more openings 34 (Figure 10 and Figure 11) in the fugitive coating 30.Fugitive coating 30 is removed after implementing second process technology.Fugitive coating can remove before or after forming entering hole 140.Although clearly do not illustrate this ad hoc approach, fugitive coating 30 shown in Figure 3 can be plated on the structure coating shown in Figure 12, and can implement Figure 16 and procedure of processing shown in Figure 17 via two coatings 30,54.As stated; Fugitive coating 30 is as the processing protective cover (machining mask) that forms passage; And for this method, the edge that helps to make the cooling duct 130 of formation on the interface between the structure coating 56 (Figure 18) of structure coating 54 and follow-up plating, to have necessary sharp keen and sharp outline.
Consult Fig. 2 and describe parts 100 embodiment of the present invention to Figure 15 and Figure 20 to Fig. 8, Figure 13.As shown in the figure, for example in Fig. 2, parts 100 comprise substrate 110, and it comprises outer surface 112 and inner surface 116.As shown in the figure, for example in Fig. 2, inner surface 116 is provided with at least one internal cavities 114.As shown in the figure, for example in Figure 19 and Figure 20, outer surface 112 is provided with one or more grooves 132, its at least part extend and have a bottom 134 along the outer surface of substrate 110 112.As shown in the figure, for example in Fig. 4, each groove 132 is characterised in that, the radius R of sidewall 135 is in the scope of 0＜R＜0.127 millimeter.If groove 132 is to use above-mentioned hybrid process method to form, then after first process operation, initial sidewall radius R can be in the scope of 0＜R＜0.254 millimeter.Carry out second process operation and can reduce radius R, the radius R of such sidewall that obtains 135 is in the scope of 0＜R＜0.127 millimeter.For example, use liquid to spray the preliminary groove of formation and can make that the sidewall radius is relatively large, can reduce (removing in some cases) this radius and carry out follow-up milling EDM operation.
The bottom 134 of corresponding recesses 132 is passed in one or more entering hole 140, is communicated with so that groove 132 flows with internal cavities 114, like Fig. 5 and shown in Figure 8.As stated, getting into hole 140 can perhaps can spend an angle of 90 degrees boring for 134 one-tenth 20 with the bottom of groove 132 and form perpendicular to the bottom 134 (like Fig. 5 and shown in Figure 8) of corresponding recesses 132.
Like Fig. 2 and shown in Figure 19; Said parts further comprise coating 150; It is arranged at least a portion of outer surface 112 of substrate 110, and on groove 132, extends, so that groove 132 is formed for one or more passages 130 of cooling-part 100 with coating 150.Particularly, the radius R of sidewall 135 (for example, like Fig. 3, Figure 10, Figure 13 and shown in Figure 16) is in the scope of 0＜R＜0.0508 millimeter.Advantageously, compare with the groove that only uses single abrasion water-jet processing method to form, the variation of the groove-groove of this groove 132 is less, controls the sidewall radius R to a greater extent because polishing operation can be implemented in.For example, the variation of the groove-groove of sidewall radius R is about 50% less than the target rated value, exactly, and less than about 20% of target rated value.For Figure 19 and layout shown in Figure 20, groove passes first structure coating 54, and it is said to Figure 15 to consult Figure 13 like preceding text.For other layouts, groove 132 does not pass structure coating, and it is said to Fig. 5 to consult Fig. 3 like preceding text.
For structure instance shown in Figure 8, the top 136 of this groove is wider than in the bottom 134 of each groove 136, so that each groove 132 curved in comprising (reentrant shaped) groove 132.Introversion connected in star such as preceding text consult Fig. 6 and Fig. 8 is said.
For Figure 19 and particular configuration shown in Figure 20, coating 150 comprises first and second structure coatings 54,56 at least.Shown in figure 20; First structure coating 54 does not extend on groove 132; And second structure coating 56 is arranged on first structure coating (54) and upward and on groove 132 extends, so that the groove 132 and second structure coating 56 constitute one or more cooling ducts 130 together.
Consult Figure 18 describes parts 100 of the present invention to Figure 21 another embodiment.As shown in the figure, for example in Figure 21, parts 100 comprise the substrate 110 with outer surface 112 and inner surface 116.As shown in the figure, for example in Figure 21, inner surface 116 is provided with at least one internal cavities 114.As shown in the figure, for example, in Figure 18 and Figure 21, parts 100 further comprise structure coating 54, and it is arranged at least a portion of outer surface 112 of substrate 110.Shown in figure 18, structure coating 54 is provided with one or more grooves 132.For Figure 19 and structure shown in Figure 20, each groove 132 part at least extends and has a bottom 134 along substrate 110.Each groove (132) is characterised in that, the radius R of sidewall 135 (Figure 16) is in the scope of 0＜R＜0.127 millimeter, with the variations to parts 100 strict control groove-grooves.As stated, groove can be completed in structure coating 54, and is said to Figure 18 like Figure 16, perhaps may extend in the substrate 110.Groove and the technology that is used to form groove are as stated.For the structure instance, groove is curved in becoming, and consults Fig. 6 to shown in Figure 8 like preceding text.
The bottom 134 of corresponding recesses 132 is passed in one or more entering hole 140, is communicated with so that groove 132 flows with internal cavities 114, and is shown in figure 18.As stated, getting into hole 140 can perhaps can spend an angle of 90 degrees boring for 134 one-tenth 20 with the bottom of groove 132 and form perpendicular to the bottom 134 (shown in figure 18) of corresponding recesses 132.
Shown in figure 18, parts 100 further comprise at least one additional coatings 56, its be arranged on the structure coating 54 with groove 132 on so that groove 132 and additional coatings 56 are formed for one or more passages 130 of cooling-part 100 together.As shown in the figure, for example in Figure 19 and Figure 20, at least one outlet opening 142 passes the additional coatings 56 of each passage 132, to obtain (or reception) from respective channel 130 and to discharge coolant fluid.Particularly, the radius R of sidewall 135 is in the scope of 0＜R＜0.0508 millimeter.This layout is shown in figure 18.
As stated, based on the accurate processing of milling EDM, the speed (therefore having reduced manufacturing cost) that above-mentioned hybrid process method provides abrasion liquid to spray.In this way, the inventive method can be used for producing on passage/coating interface and has the cooling-part of required sharp edge, thereby helps with free from flaw mode plating first metal (structure) coating.
Although only illustrate and described some characteristic of the present invention in this manual, the those skilled in the art can carry out multiple modification and variation to the present invention.Therefore, should be understood that the appended claims intention comprises all this type of modification and variations in the spirit of the present invention.
Claims (10)
1. method that in parts (100), forms one or more grooves (132), said method comprises:
Use first process technology in the outer surface (112) of substrate (110), to form one or more preliminary grooves (131); Each groove in wherein said one or more preliminary grooves (131) has bottom (134); And part is extended along the said outer surface (112) of said substrate (110) at least; And wherein said substrate (110) has inner surface (116), and said inner surface is provided with at least one internal cavities (114);
Use second process technology that said one or more preliminary grooves (131) are further processed, to form corresponding one or more groove (132); And
Form one or more entering hole (140), it passes the said bottom (134) of the corresponding recesses in the said groove (132), thereby the respective inner cavity in said corresponding recesses (132) and said at least one internal cavities (114) is connected with the stream mode of communicating.
2. method according to claim 1; It is characterized in that; Further be included in the said outer surface (112) of said substrate (110) and form said one or more preliminary grooves (131) before; Cast said substrate (110), wherein said first process technology comprises that abrasion liquid sprays, and wherein said one or more preliminary grooves (112) are gone up formation through the said outer surface (160) that makes abrasion liquid jet (160) act on said substrate (110).
3. method according to claim 2; It is characterized in that said second process technology is by selecting in following the group that forms: the spark machined (milling EDM) and the Laser Processing (laser drill) of electrochemistry processing (ECM), electrical discharge machining (EDM), use rotation electrode (165).
4. method according to claim 2; It is characterized in that; Each groove in said one or more groove (132) has top (136); Wherein use each groove in said one or more preliminary grooves (131) that said abrasion liquid jet (160) forms to have the bottom (234) of being wider than said top (236); So that each groove in said one or more preliminary grooves (131) comprise in curved preliminary groove (131), and the said bottom (134) of wherein said groove (132) is wider than said top (136), so that each groove in said one or more groove (132) comprises introversion connected in star (132).
5. method according to claim 1; It is characterized in that; Further be included in and form said one or more preliminary grooves (131) before, structure coating (54) is plated on the said outer surface (112) of said substrate (110), the formation method of wherein said one or more preliminary grooves (131) is; Implement said first process technology processing, thereby in said structure coating (54), form one or more openings (58) via said structure coating (54); And the formation method of wherein said one or more groove (132) is to implement said second process technology via the said one or more openings (58) in the said structure coating (54).
6. method that in parts (100), forms one or more grooves (132), said method comprises:
Structure coating (54) is plated on the outer surface (112) of substrate (110), wherein said substrate (110) has at least one internal cavities (114);
Use first process technology in said structure coating (54), to form one or more preliminary grooves (131), each groove in wherein said one or more preliminary grooves (131) has bottom (134), and part is extended along said substrate (110) at least;
Use second process technology that said one or more preliminary grooves (131) are further processed, in said structure coating (54), to form corresponding one or more grooves (132); And
Form one or more entering hole (140), it passes the said bottom (134) of the corresponding recesses in the said groove (132), thereby the respective inner cavity in said corresponding recesses (132) and said at least one internal cavities (114) is connected with the stream mode of communicating.
7. method according to claim 6; It is characterized in that; Further be included in the said structure coating (54) and form one or more preliminary grooves (131) before; Cast said substrate (110), wherein said first process technology comprises that abrasion liquid sprays, and wherein said one or more preliminary grooves (131) are gone up formation through making abrasion liquid jet (160) act on said structure coating (54); And wherein said second process technology is by selecting in following the group that forms: the spark machined milling (EDM) of electrochemistry processing (ECM), electrical discharge machining (EDM), use rotation electrode, and Laser Processing (laser drill).
8. parts (100) comprising:
The substrate (110) that comprises outer surface (112) and inner surface (116); Wherein said inner surface (116) is provided with at least one internal cavities (114); Wherein said outer surface (112) is provided with one or more grooves (132); Each groove in wherein said one or more groove (132) part at least extends and has a bottom (134) along the said outer surface (112) of said substrate (110); Wherein each groove (132) is characterised in that; Sidewall (135) radius R is in the scope of 0＜R＜0.127 millimeter, and wherein one or more get into the bottom (134) that the corresponding recesses in said one or more groove (132) is passed in holes (140), so that said groove (132) is communicated with respective inner cavity flow in said at least one internal cavities (114); And
Coating (150); It is plated at least a portion of said outer surface (112) of said substrate (110); And go up extension at said one or more grooves (132), so that said one or more groove (132) and said coating (150) are configured for cooling off one or more passages (130) of said parts (100) together.
9. parts (100) comprising:
Comprise the substrate (110) of outer surface (112) and inner surface (116), wherein said inner surface (116) is provided with at least one internal cavities (114);
Structure coating (54); It is arranged at least a portion of said outer surface (112) of said substrate (110); Wherein said structure coating (54) is provided with one or more grooves (132); Each groove in wherein said one or more groove (132) is at least partly along said substrate (110) extension and bottom having (134); And wherein one or more get into the bottom (134) that the corresponding recesses in said one or more groove (132) is passed in hole (140); So that said groove (132) is communicated with respective inner cavity flow in said at least one internal cavities (114), wherein each groove (132) is characterised in that, sidewall (135) radius R is in the scope of 0＜R＜0.127 millimeter; And
At least one additional coatings (56); It is arranged on said structure coating (54) go up with said one or more grooves (132) on; So that said one or more groove (132) and said additional coatings (56) are formed for cooling off one or more passages (130) of said parts (100) together; Wherein at least one outlet opening (142) passes the said additional coatings (56) of each passage in corresponding one or more passage (132), to obtain and to discharge coolant fluid from said respective channel (130).
10. parts according to claim 25 (100) is characterized in that, said additional coatings (56) comprises second structure coating (56), and wherein said groove (132) passes said structure coating (54) and extends in the said substrate (110).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/110,080 US20120295061A1 (en) | 2011-05-18 | 2011-05-18 | Components with precision surface channels and hybrid machining method |
| US13/110080 | 2011-05-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102785058A true CN102785058A (en) | 2012-11-21 |
Family
ID=46146715
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210166868XA Pending CN102785058A (en) | 2011-05-18 | 2012-05-18 | components with precision surface channels and hybrid machining method |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20120295061A1 (en) |
| EP (1) | EP2525044A2 (en) |
| CN (1) | CN102785058A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103551813A (en) * | 2013-11-11 | 2014-02-05 | 中国南方航空工业(集团)有限公司 | Machining method for plasma-sprayed surface of internal annular surface of annular housing |
| CN104907650A (en) * | 2015-05-26 | 2015-09-16 | 南京航空航天大学 | Abrasive water jet-electrolysis composite pass making method and device for metal part with thermal barrier coating |
| CN105965067A (en) * | 2015-03-12 | 2016-09-28 | 通用电气公司 | Machining tool positioning template for airfoil |
| CN107560576A (en) * | 2017-08-07 | 2018-01-09 | 苏州电加工机床研究所有限公司 | Machining method for on-machine detection and deviation correction of numerical control electric spark small hole of turbine blade |
| CN108736024A (en) * | 2018-06-05 | 2018-11-02 | 德州新动能铁塔发电有限公司 | A kind of fuel cell system reformer chamber and fuel cell system |
| CN113698085A (en) * | 2021-07-05 | 2021-11-26 | 维达力实业（赤壁）有限公司 | Processing method of clearance groove and 3D substrate product |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120243995A1 (en) * | 2011-03-21 | 2012-09-27 | General Electric Company | Components with cooling channels formed in coating and methods of manufacture |
| JP5996260B2 (en) * | 2012-05-09 | 2016-09-21 | 株式会社ディスコ | Workpiece division method |
| EP3068994B1 (en) | 2013-11-15 | 2019-08-07 | United Technologies Corporation | Component with embedded sensor |
| EP3068580B1 (en) | 2013-11-15 | 2020-09-02 | United Technologies Corporation | Fluidic machining method and system |
| US20150147479A1 (en) * | 2013-11-22 | 2015-05-28 | General Electric Company | Methods for the formation of cooling channels, and related articles of manufacture |
| US9243511B2 (en) * | 2014-02-25 | 2016-01-26 | Siemens Aktiengesellschaft | Turbine abradable layer with zig zag groove pattern |
| WO2015130528A1 (en) | 2014-02-25 | 2015-09-03 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with crack isolating engineered surface features |
| US9151175B2 (en) | 2014-02-25 | 2015-10-06 | Siemens Aktiengesellschaft | Turbine abradable layer with progressive wear zone multi level ridge arrays |
| WO2016133583A1 (en) | 2015-02-18 | 2016-08-25 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having ridges with holes |
| EP3259452A2 (en) | 2015-02-18 | 2017-12-27 | Siemens Aktiengesellschaft | Forming cooling passages in combustion turbine superalloy castings |
| CN108699914A (en) * | 2016-02-19 | 2018-10-23 | 西门子股份公司 | Mixed component with cooling duct and corresponding method |
| US10519780B2 (en) * | 2016-09-13 | 2019-12-31 | Rolls-Royce Corporation | Dual-walled components for a gas turbine engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5354961A (en) * | 1992-02-12 | 1994-10-11 | Charmilles Technologies S.A. | Device and process for electrical-discharge machining of a three-dimensional cavity with a thin rotating tool electrode |
| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| US5747769A (en) * | 1995-11-13 | 1998-05-05 | General Electric Company | Method of laser forming a slot |
| US5817372A (en) * | 1997-09-23 | 1998-10-06 | General Electric Co. | Process for depositing a bond coat for a thermal barrier coating system |
| CN1658995A (en) * | 2002-06-12 | 2005-08-24 | 阿尔斯通技术有限公司 | Method of producing a composite component |
| US20060099080A1 (en) * | 2004-11-09 | 2006-05-11 | General Electric Company | Methods and apparatus for cooling gas turbine engine components |
| US20090311416A1 (en) * | 2008-06-17 | 2009-12-17 | General Electric Company | Method and system for machining a profile pattern in ceramic coating |
| US20100078418A1 (en) * | 2008-09-26 | 2010-04-01 | Electro Scientific Industries, Inc. | Method of laser micro-machining stainless steel with high cosmetic quality |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3457619A (en) * | 1967-11-28 | 1969-07-29 | Gen Electric | Production of perforated metallic bodies |
| US5626462A (en) | 1995-01-03 | 1997-05-06 | General Electric Company | Double-wall airfoil |
| JP3529191B2 (en) | 1995-04-26 | 2004-05-24 | 日本精工株式会社 | Method of manufacturing spherical roller bearing with cage and cage for spherical roller bearing with cage |
| US6644921B2 (en) | 2001-11-08 | 2003-11-11 | General Electric Company | Cooling passages and methods of fabrication |
| US7351290B2 (en) | 2003-07-17 | 2008-04-01 | General Electric Company | Robotic pen |
| JP4931507B2 (en) * | 2005-07-26 | 2012-05-16 | スネクマ | Cooling flow path formed in the wall |
| US7879203B2 (en) | 2006-12-11 | 2011-02-01 | General Electric Company | Method and apparatus for cathodic arc ion plasma deposition |
| US8739404B2 (en) * | 2010-11-23 | 2014-06-03 | General Electric Company | Turbine components with cooling features and methods of manufacturing the same |
| US8727727B2 (en) * | 2010-12-10 | 2014-05-20 | General Electric Company | Components with cooling channels and methods of manufacture |
| US8528208B2 (en) * | 2011-04-11 | 2013-09-10 | General Electric Company | Methods of fabricating a coated component using multiple types of fillers |
| US8601691B2 (en) * | 2011-04-27 | 2013-12-10 | General Electric Company | Component and methods of fabricating a coated component using multiple types of fillers |
-
2011
- 2011-05-18 US US13/110,080 patent/US20120295061A1/en not_active Abandoned
-
2012
- 2012-05-17 EP EP20120168445 patent/EP2525044A2/en not_active Withdrawn
- 2012-05-18 CN CN201210166868XA patent/CN102785058A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5354961A (en) * | 1992-02-12 | 1994-10-11 | Charmilles Technologies S.A. | Device and process for electrical-discharge machining of a three-dimensional cavity with a thin rotating tool electrode |
| US5640767A (en) * | 1995-01-03 | 1997-06-24 | Gen Electric | Method for making a double-wall airfoil |
| US5747769A (en) * | 1995-11-13 | 1998-05-05 | General Electric Company | Method of laser forming a slot |
| US5817372A (en) * | 1997-09-23 | 1998-10-06 | General Electric Co. | Process for depositing a bond coat for a thermal barrier coating system |
| CN1658995A (en) * | 2002-06-12 | 2005-08-24 | 阿尔斯通技术有限公司 | Method of producing a composite component |
| US20060099080A1 (en) * | 2004-11-09 | 2006-05-11 | General Electric Company | Methods and apparatus for cooling gas turbine engine components |
| US20090311416A1 (en) * | 2008-06-17 | 2009-12-17 | General Electric Company | Method and system for machining a profile pattern in ceramic coating |
| US20100078418A1 (en) * | 2008-09-26 | 2010-04-01 | Electro Scientific Industries, Inc. | Method of laser micro-machining stainless steel with high cosmetic quality |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103551813A (en) * | 2013-11-11 | 2014-02-05 | 中国南方航空工业(集团)有限公司 | Machining method for plasma-sprayed surface of internal annular surface of annular housing |
| CN105965067A (en) * | 2015-03-12 | 2016-09-28 | 通用电气公司 | Machining tool positioning template for airfoil |
| CN105965067B (en) * | 2015-03-12 | 2020-04-28 | 通用电气公司 | Machining tool locating template for airfoil |
| CN104907650A (en) * | 2015-05-26 | 2015-09-16 | 南京航空航天大学 | Abrasive water jet-electrolysis composite pass making method and device for metal part with thermal barrier coating |
| CN107560576A (en) * | 2017-08-07 | 2018-01-09 | 苏州电加工机床研究所有限公司 | Machining method for on-machine detection and deviation correction of numerical control electric spark small hole of turbine blade |
| CN107560576B (en) * | 2017-08-07 | 2019-12-03 | 苏州电加工机床研究所有限公司 | Machining method for on-machine detection and deviation correction of numerical control electric spark small hole of turbine blade |
| CN108736024A (en) * | 2018-06-05 | 2018-11-02 | 德州新动能铁塔发电有限公司 | A kind of fuel cell system reformer chamber and fuel cell system |
| CN113698085A (en) * | 2021-07-05 | 2021-11-26 | 维达力实业（赤壁）有限公司 | Processing method of clearance groove and 3D substrate product |
| CN113698085B (en) * | 2021-07-05 | 2022-05-20 | 维达力实业（赤壁）有限公司 | Method for processing clearance groove and 3D substrate product |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2525044A2 (en) | 2012-11-21 |
| US20120295061A1 (en) | 2012-11-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102785058A (en) | components with precision surface channels and hybrid machining method | |
| CN102953828B (en) | Component and manufacture method with cooling duct | |
| JP6537162B2 (en) | Part with multi-layer cooling features and method of manufacture | |
| CN102606231B (en) | There is component and the manufacture method of cooling channel | |
| US9598963B2 (en) | Components with microchannel cooling | |
| JP5916079B2 (en) | Method for manufacturing a component using a two-layer coating | |
| EP2487330B1 (en) | Components with cooling channels and methods of manufacture | |
| CN102839992B (en) | With component and the manufacture method of cooling channel | |
| CN102691533A (en) | Components with cooling channels formed in coating and methods of manufacture | |
| CN103161522A (en) | Gas turbine components with microchannel cooling | |
| CN103056604A (en) | Components with laser cladding and methods of manufacture | |
| US9249672B2 (en) | Components with cooling channels and methods of manufacture | |
| JP2014224526A (en) | Components with double sided cooling features and methods of manufacturing the same | |
| EP2537636B1 (en) | Component with cooling channels and method of manufacture | |
| JP2014087924A (en) | Components with micro cooled coating layer and methods of manufacture | |
| EP2573320A2 (en) | Components with cooling channels and methods of manufacture | |
| JP6254820B2 (en) | Component with microcooled patterning coating layer and method of manufacturing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121121 |